Abstract: A blade, for a gas turbine, includes a blade airfoil, having a shroud segment arranged on its upper end. The shroud segment together with shroud segments of other blades of a blade row forming an annular shroud which delimits hot gas passage of the gas turbine, and said shroud segment, on sides on which it adjoins adjacent shroud segments of the annular shroud, is provided with upwardly projecting side rails which extend along a side edge, to improve sealing to the hot gas passage. The side rails include rail-parallel or essentially rail-parallel, upwardly open slots through which cooling air, which is introduced via the shroud segment from an interior of the blade airfoil, discharges into the space above the shroud segment.

Abstract: A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.

Abstract: In a non-destructive method for determining the internal structure of a heat conducting body, such as a cooling structure of a turbine blade, a flow medium is passed through the internal structure and the resultant thermal image on an external surface of the body is registered using a pixelised thermal image detector. Heat transfer coefficients and wall thicknesses of the internal structure are determined by means of a 1-,2-, or 3-dimensional inverse method that includes the numerical modelling of the surface temperatures using initial values for heat transfer coefficients and wall thicknesses and an optimization of the values using an iteration method. In a special variant of the method, the spatial geometry of the internal structure of the body is determined by means of the same inverse method and a geometry model that is optimised by iteration. No prior knowledge of the internal geometry is required.

Abstract: A blade, for a gas turbine, includes a blade airfoil, having a shroud segment arranged on its upper end. The shroud segment together with shroud segments of other blades of a blade row forming an annular shroud which delimits hot gas passage of the gas turbine, and said shroud segment, on sides on which it adjoins adjacent shroud segments of the annular shroud, is provided with upwardly projecting side rails which extend along a side edge, to improve sealing to the hot gas passage. The side rails include rail-parallel or essentially rail-parallel, upwardly open slots through which cooling air, which is introduced via the shroud segment from an interior of the blade airfoil, discharges into the space above the shroud segment.

Abstract: A gas turbine including an inner casing and a rotor having rotatable blades with a shroud and a fin, and a cooling arrangement arranged in a cavity in the casing and about the rotatable blade. The blade shroud includes a protrusion extending away from the blade leading edge into the cavity and openings in the cavity wall for a cooling fluid. The protrusion is defined by angles in relation to the flow channel wall. The protrusion affects a vortex flow of cooling fluid entering through the openings and a vortex flow of hot gas entering from the flow channel into the cavity. The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.

Abstract: In a non-destructive method for determining the internal structure of a heat conducting body, such as a cooling structure of a turbine blade, a flow medium is passed through the internal structure and the resultant thermal image on an external surface of the body is registered using a pixelised thermal image detector. Heat transfer coefficients and wall thicknesses of the internal structure are determined by means of a 1-,2-, or 3-dimensional inverse method that includes the numerical modelling of the surface temperatures using initial values for heat transfer coefficients and wall thicknesses and an optimisation of the values using an iteration method. In a special variant of the method, the spatial geometry of the internal structure of the body is determined by means of the same inverse method and a geometry model that is optimised by iteration. No prior knowledge of the internal geometry is required.